BR0103410B1 - method of manufacturing a rotor assembly as well as rotor assembly. - Google Patents

method of manufacturing a rotor assembly as well as rotor assembly.

Info

Publication number
BR0103410B1
BR0103410B1 BRPI0103410-3A BR0103410A BR0103410B1 BR 0103410 B1 BR0103410 B1 BR 0103410B1 BR 0103410 A BR0103410 A BR 0103410A BR 0103410 B1 BR0103410 B1 BR 0103410B1
Authority
BR
Brazil
Prior art keywords
rotor assembly
manufacturing
well
rotor
assembly
Prior art date
Application number
BRPI0103410-3A
Other languages
Portuguese (pt)
Other versions
BR0103410A (en
Inventor
Stephen Michael Carter
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed filed Critical
Publication of BR0103410A publication Critical patent/BR0103410A/en
Publication of BR0103410B1 publication Critical patent/BR0103410B1/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/713—Shape curved inflexed

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
BRPI0103410-3A 2000-08-21 2001-08-16 method of manufacturing a rotor assembly as well as rotor assembly. BR0103410B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US09/643,012 US6524070B1 (en) 2000-08-21 2000-08-21 Method and apparatus for reducing rotor assembly circumferential rim stress

Publications (2)

Publication Number Publication Date
BR0103410A BR0103410A (en) 2002-03-26
BR0103410B1 true BR0103410B1 (en) 2010-06-29

Family

ID=24579000

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0103410-3A BR0103410B1 (en) 2000-08-21 2001-08-16 method of manufacturing a rotor assembly as well as rotor assembly.

Country Status (5)

Country Link
US (1) US6524070B1 (en)
EP (1) EP1182328A3 (en)
JP (1) JP4636746B2 (en)
BR (1) BR0103410B1 (en)
CA (1) CA2354834C (en)

Families Citing this family (47)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6669445B2 (en) * 2002-03-07 2003-12-30 United Technologies Corporation Endwall shape for use in turbomachinery
US6837685B2 (en) * 2002-12-13 2005-01-04 General Electric Company Methods and apparatus for repairing a rotor assembly of a turbine
FR2851798B1 (en) * 2003-02-27 2005-04-29 Snecma Moteurs TURBOREACTOR TURBINE BOW
US6857853B1 (en) * 2003-08-13 2005-02-22 General Electric Company Conical tip shroud fillet for a turbine bucket
US6905309B2 (en) * 2003-08-28 2005-06-14 General Electric Company Methods and apparatus for reducing vibrations induced to compressor airfoils
GB2411441B (en) * 2004-02-24 2006-04-19 Rolls Royce Plc Fan or compressor blisk
DE102004026386A1 (en) * 2004-05-29 2005-12-22 Mtu Aero Engines Gmbh Airfoil of a turbomachine and turbomachine
US7249928B2 (en) * 2005-04-01 2007-07-31 General Electric Company Turbine nozzle with purge cavity blend
US7476086B2 (en) * 2005-04-07 2009-01-13 General Electric Company Tip cambered swept blade
US7374403B2 (en) * 2005-04-07 2008-05-20 General Electric Company Low solidity turbofan
US7497664B2 (en) * 2005-08-16 2009-03-03 General Electric Company Methods and apparatus for reducing vibrations induced to airfoils
US7465155B2 (en) 2006-02-27 2008-12-16 Honeywell International Inc. Non-axisymmetric end wall contouring for a turbomachine blade row
JP5283855B2 (en) * 2007-03-29 2013-09-04 株式会社Ｉｈｉ Turbomachine wall and turbomachine
US8100655B2 (en) * 2008-03-28 2012-01-24 Pratt & Whitney Canada Corp. Method of machining airfoil root fillets
EP2184442A1 (en) * 2008-11-11 2010-05-12 ALSTOM Technology Ltd Airfoil fillet
US8231353B2 (en) * 2008-12-31 2012-07-31 General Electric Company Methods and apparatus relating to improved turbine blade platform contours
JP5297228B2 (en) * 2009-02-26 2013-09-25 三菱重工業株式会社 Turbine blade and gas turbine
FR2946083B1 (en) * 2009-05-28 2011-06-17 Snecma LOW PRESSURE TURBINE
US8439643B2 (en) * 2009-08-20 2013-05-14 General Electric Company Biformal platform turbine blade
US8403645B2 (en) * 2009-09-16 2013-03-26 United Technologies Corporation Turbofan flow path trenches
US8435006B2 (en) * 2009-09-30 2013-05-07 Rolls-Royce Corporation Fan
US9976433B2 (en) 2010-04-02 2018-05-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured rotor blade platform
US8904636B2 (en) 2011-07-22 2014-12-09 Pratt & Whitney Canada Corp. Method of fabricating integrally bladed rotor using surface positioning in relation to surface priority
US8844132B2 (en) 2011-07-22 2014-09-30 Pratt & Whitney Canada Corp. Method of machining using an automatic tool path generator adapted to individual blade surfaces on an integrally bladed rotor
US8788083B2 (en) * 2011-07-22 2014-07-22 Pratt & Whitney Canada Corp. Compensation for process variables in a numerically-controlled machining operation
US8631577B2 (en) 2011-07-22 2014-01-21 Pratt & Whitney Canada Corp. Method of fabricating integrally bladed rotor and stator vane assembly
CN103796762B (en) * 2011-11-04 2016-08-24 日本精工株式会社 Main shaft device and electrostatic spraying apparatus
US9267386B2 (en) 2012-06-29 2016-02-23 United Technologies Corporation Fairing assembly
WO2014028056A1 (en) 2012-08-17 2014-02-20 United Technologies Corporation Contoured flowpath surface
US20140154068A1 (en) * 2012-09-28 2014-06-05 United Technologies Corporation Endwall Controuring
WO2014163673A2 (en) 2013-03-11 2014-10-09 Bronwyn Power Gas turbine engine flow path geometry
JP5479624B2 (en) * 2013-03-13 2014-04-23 三菱重工業株式会社 Turbine blade and gas turbine
WO2014197062A2 (en) 2013-03-15 2014-12-11 United Technologies Corporation Fan exit guide vane platform contouring
US10352180B2 (en) 2013-10-23 2019-07-16 General Electric Company Gas turbine nozzle trailing edge fillet
US10294805B2 (en) * 2013-12-20 2019-05-21 United Technologies Corporation Gas turbine engine integrally bladed rotor with asymmetrical trench fillets
GB201418948D0 (en) * 2014-10-24 2014-12-10 Rolls Royce Plc Row of aerofoil members
US9890641B2 (en) 2015-01-15 2018-02-13 United Technologies Corporation Gas turbine engine truncated airfoil fillet
US20160245297A1 (en) * 2015-02-23 2016-08-25 Howden Roots Llc Impeller comprising variably-dimensioned fillet to secure blades and compressor comprised thereof
US20170089202A1 (en) * 2015-09-29 2017-03-30 United Technologies Corporation Flow path trenches and methods of forming the same
US10240462B2 (en) 2016-01-29 2019-03-26 General Electric Company End wall contour for an axial flow turbine stage
US10458426B2 (en) 2016-09-15 2019-10-29 General Electric Company Aircraft fan with low part-span solidity
US10502230B2 (en) * 2017-07-18 2019-12-10 United Technologies Corporation Integrally bladed rotor having double fillet
DE102017218886A1 (en) * 2017-10-23 2019-04-25 MTU Aero Engines AG Shovel and rotor for a turbomachine and turbomachine
US20190178094A1 (en) * 2017-11-02 2019-06-13 United Technologies Corporation Integrally bladed rotor
CN108487938A (en) * 2018-04-25 2018-09-04 哈尔滨电气股份有限公司 A kind of novel combustion engine turbine first order movable vane
FR3106626B1 (en) * 2020-01-24 2022-06-10 Safran Aircraft Engines DIFFERENTIATED SWITCHING BETWEEN ROTOR AND STATOR AT ROTOR-STATOR AIR GATES IN A TURBOMACHINE COMPRESSOR
FR3106627B1 (en) * 2020-01-24 2023-03-17 Safran Aircraft Engines WAVE TIPPING AT ROTOR-STATOR AIR GAP IN A TURBOMACHINE COMPRESSOR

Family Cites Families (48)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2735612A (en) 1956-02-21 hausmann
US1793468A (en) 1929-05-28 1931-02-24 Westinghouse Electric & Mfg Co Turbine blade
CH229266A (en) * 1942-03-26 1943-10-15 Sulzer Ag Turbomachine, the blade surfaces of which merge into the base surface with a rounding at the blade root.
US2429324A (en) 1943-12-30 1947-10-21 Meisser Christian Rotor for centrifugal compressors
US2415380A (en) 1944-11-15 1947-02-04 Weber Max Propeller blade
US2790620A (en) 1952-07-09 1957-04-30 Gen Electric Multiple finger dovetail attachment for turbine bucket
US2918254A (en) 1954-05-10 1959-12-22 Hausammann Werner Turborunner
US3095180A (en) 1959-03-05 1963-06-25 Stalker Corp Blades for compressors, turbines and the like
FR1442526A (en) 1965-05-07 1966-06-17 Rateau Soc Improvements to curved canals traversed by gas or vapor
GB1119392A (en) 1966-06-03 1968-07-10 Rover Co Ltd Axial flow rotor for a turbine or the like
US3481531A (en) 1968-03-07 1969-12-02 United Aircraft Canada Impeller boundary layer control device
US3584969A (en) 1968-05-25 1971-06-15 Aisin Seiki Flexible blade fan
FR1602965A (en) * 1968-08-16 1971-03-01
GB1302036A (en) 1969-06-26 1973-01-04
US3661475A (en) 1970-04-30 1972-05-09 Gen Electric Turbomachinery rotors
US3890062A (en) 1972-06-28 1975-06-17 Us Energy Blade transition for axial-flow compressors and the like
US3927952A (en) 1972-11-20 1975-12-23 Garrett Corp Cooled turbine components and method of making the same
US3951611A (en) 1974-11-14 1976-04-20 Morrill Wayne J Blank for fan blade
NO146029C (en) 1976-08-11 1982-07-14 Kongsberg Vapenfab As IMPELLER ELEMENT IN A RADIAL GAS TURBINE WHEEL
US4135857A (en) * 1977-06-09 1979-01-23 United Technologies Corporation Reduced drag airfoil platforms
SU756083A1 (en) 1978-07-18 1980-08-15 Vladislav D Lubenets Vortex-type machine impeller
US4335997A (en) 1980-01-16 1982-06-22 General Motors Corporation Stress resistant hybrid radial turbine wheel
DE3023466C2 (en) 1980-06-24 1982-11-25 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Device for reducing secondary flow losses in a bladed flow channel
US4671739A (en) 1980-07-11 1987-06-09 Robert W. Read One piece molded fan
JPS57167203U (en) * 1981-04-17 1982-10-21
DE3202855C1 (en) 1982-01-29 1983-03-31 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Device for reducing secondary flow losses in a bladed flow channel
US4587700A (en) 1984-06-08 1986-05-13 The Garrett Corporation Method for manufacturing a dual alloy cooled turbine wheel
US4659288A (en) 1984-12-10 1987-04-21 The Garrett Corporation Dual alloy radial turbine rotor with hub material exposed in saddle regions of blade ring
DE3514122A1 (en) 1985-04-19 1986-10-23 MAN Gutehoffnungshütte GmbH, 4200 Oberhausen METHOD FOR PRODUCING A GUIDE BLADE FOR A TURBINE OR COMPRESSOR LEAD, AND GUIDE BLADE PRODUCED BY THE METHOD
DE3710321C1 (en) 1987-03-28 1988-06-01 Mtu Muenchen Gmbh Fan blade, especially for prop fan engines
DE3726522A1 (en) 1987-08-10 1989-02-23 Standard Elektrik Lorenz Ag FAN WHEEL MADE FROM A METAL SHEET AND METHOD FOR THE PRODUCTION THEREOF
US4866985A (en) 1987-09-10 1989-09-19 United States Of America As Represented By The Secretary Of Interior Bucket wheel assembly for a flow measuring device
US5018271A (en) 1988-09-09 1991-05-28 Airfoil Textron Inc. Method of making a composite blade with divergent root
US5061154A (en) 1989-12-11 1991-10-29 Allied-Signal Inc. Radial turbine rotor with improved saddle life
GB2251897B (en) 1991-01-15 1994-11-30 Rolls Royce Plc A rotor
US5215439A (en) 1991-01-15 1993-06-01 Northern Research & Engineering Corp. Arbitrary hub for centrifugal impellers
US5397215A (en) * 1993-06-14 1995-03-14 United Technologies Corporation Flow directing assembly for the compression section of a rotary machine
GB2281356B (en) 1993-08-20 1997-01-29 Rolls Royce Plc Gas turbine engine turbine
US5554004A (en) 1995-07-27 1996-09-10 Ametek, Inc. Fan impeller assembly
FR2738303B1 (en) 1995-08-30 1997-11-28 Europ Propulsion TURBINE OF THERMOSTRUCTURAL COMPOSITE MATERIAL, IN PARTICULAR WITH A SMALL DIAMETER, AND METHOD FOR THE PRODUCTION THEREOF
US5735673A (en) 1996-12-04 1998-04-07 United Technologies Corporation Turbine engine rotor blade pair
DE19650656C1 (en) * 1996-12-06 1998-06-10 Mtu Muenchen Gmbh Turbo machine with transonic compressor stage
ATE228609T1 (en) * 1997-04-01 2002-12-15 Siemens Ag SURFACE STRUCTURE FOR THE WALL OF A FLOW CHANNEL OR TURBINE BLADE
EP0943784A1 (en) * 1998-03-19 1999-09-22 Asea Brown Boveri AG Contoured channel for an axial turbomachine
GB9823840D0 (en) * 1998-10-30 1998-12-23 Rolls Royce Plc Bladed ducting for turbomachinery
US6217283B1 (en) * 1999-04-20 2001-04-17 General Electric Company Composite fan platform
US6511294B1 (en) * 1999-09-23 2003-01-28 General Electric Company Reduced-stress compressor blisk flowpath
US6561761B1 (en) * 2000-02-18 2003-05-13 General Electric Company Fluted compressor flowpath

Also Published As

Publication number Publication date
CA2354834C (en) 2009-02-10
EP1182328A2 (en) 2002-02-27
BR0103410A (en) 2002-03-26
US6524070B1 (en) 2003-02-25
EP1182328A3 (en) 2003-06-04
JP2002122002A (en) 2002-04-26
CA2354834A1 (en) 2002-02-21
JP4636746B2 (en) 2011-02-23

Similar Documents

Publication Publication Date Title
BR0103410B1 (en) method of manufacturing a rotor assembly as well as rotor assembly.
BR0105227B1 (en) method of repairing a turbine nozzle segment as well as turbine nozzle segment.
DE60138579D1 (en) Bladed rotor assembly
BR0104191B1 (en) rotor assembly for a gas turbine rotor.
DE60205413D1 (en) production method
DE60232285D1 (en) Ribbed integral rotor
BR0316982B1 (en) hydroelectric plant.
IT1319495B1 (en) PROCEDURE FOR THE CONSTRUCTION OF A ROTOR FOR COMPRESSOR-CENTRIFUGHI.
DE60036518D1 (en) axial turbines
DE60226131D1 (en) KNITTING METHOD
BR0100759B1 (en) method for manufacturing a combustor for a turbine engine, as well as coating and combustor.
BR0005204B1 (en) spiral machine, spiral member and method of manufacturing a spiral member.
ITTO20000319A0 (en) PROCEDURE FOR THE MANUFACTURE OF DEEP POCKET JOINTING STRUCTURES.
BR0312310B1 (en) process of manufacturing a body of revolution.
NO20032227D0 (en) A lactonization method
DE60130426D1 (en) Alumina-phosphor manufacturing process
ITMI20022486A1 (en) FLYER
DE50005753D1 (en) assembly method
FR2809764B1 (en) AXIAL TURBINE STAGE
NO20040515L (en) Luminescent Phosphorus.
FI20011146A0 (en) New manufacturing method
BR8003238Y1 (en) structure of a still.
SE0103679D0 (en) Wind turbines
NO20031880D0 (en) Low power, miniature hydraulic actuator
SE0102634D0 (en) Rotor

Legal Events

Date Code Title Description
B06A Patent application procedure suspended [chapter 6.1 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 16/08/2001, OBSERVADAS AS CONDICOES LEGAIS.

B21F Lapse acc. art. 78, item iv - on non-payment of the annual fees in time
B24J Lapse because of non-payment of annual fees (definitively: art 78 iv lpi, resolution 113/2013 art. 12)

Free format text: EM VIRTUDE DA EXTINCAO PUBLICADA NA RPI 2475 DE 12-06-2018 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDA A EXTINCAO DA PATENTE E SEUS CERTIFICADOS, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013.